Abstract
An L1 control augmentation is developed based on a novel autopilot structure for a highly agile, tail-controlled missile. The autopilot is designed to control the pitch and yaw accelerations in the body-fixed frame while maintaining a desired roll angle. In order to compensate for the undesirable effects of modeling uncertainty, an L1 adaptive controller with piece-wise constant adaptation laws is developed that explicitly takes into account the multi-loop dynamic structure of the autopilot. The benefits of the augmented design are demonstrated via Monte-Carlo simulations of a high-fidelity 6DOF missile model, in which a wide spectrum of uncertainty combinations is considered.
| Original language | English (US) |
|---|---|
| Title of host publication | AIAA Guidance, Navigation, and Control Conference 2012 |
| State | Published - Dec 1 2012 |
| Event | AIAA Guidance, Navigation, and Control Conference 2012 - Minneapolis, MN, United States Duration: Aug 13 2012 → Aug 16 2012 |
Publication series
| Name | AIAA Guidance, Navigation, and Control Conference 2012 |
|---|
Other
| Other | AIAA Guidance, Navigation, and Control Conference 2012 |
|---|---|
| Country | United States |
| City | Minneapolis, MN |
| Period | 8/13/12 → 8/16/12 |
ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Fingerprint Dive into the research topics of 'L1 adaptive augmentation of a missile autopilot'. Together they form a unique fingerprint.
Cite this
Peter, F., Holzapfel, F., Xargay, E., & Hovakimyan, N. (2012). L1 adaptive augmentation of a missile autopilot. In AIAA Guidance, Navigation, and Control Conference 2012 (AIAA Guidance, Navigation, and Control Conference 2012).